8610 Federal Register / Vol. 72, No. 38 / Tuesday, February 27, 2007 / Rules and Regulations 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

(3) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The Federal Aviation 

Administration (FAA) amends § 39.13 

by adding the following new 

airworthiness directive (AD): 

2007–04–27 Fokker Services B.V.: 

Amendment 39–14960. Docket No. 

FAA–2006–26044; Directorate Identifier 

2006–NM–098–AD. 

Effective Date 

(a) This AD becomes effective April 3, 

2007. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Fokker Model 

F.28 Mark 1000, 2000, 3000, and 4000 

airplanes, certificated in any category. 

Unsafe Condition 

(d) This AD results from a report of a failed 

downlock actuator, which resulted in the left 

main landing gear (MLG) collapsing during 

taxi after landing. We are issuing this AD to 

prevent failure of the downlock actuator, 

which could prevent the MLG side stay from 

locking properly, resulting in collapse of the 

MLG during ground maneuvers or upon 

landing. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Determination of the Part Number (P/N) of 

the MLG Downlock Actuators 

(f) Within 66 months after the effective 

date of this AD: Inspect the left- and righthand MLG downlock actuators to determine 

if P/N 200497005 or 200498005 is installed. 

A review of airplane maintenance records is 

acceptable in lieu of this inspection if the 

part number of the MLG downlock actuator 

can be conclusively determined from that 

review. If an MLG downlock actuator does 

not have a subject part number, no further 

action is required by this AD for that MLG 

only, except as provided by paragraph (h) of 

this AD. 

Replacement of Subject MLG Downlock 

Actuators 

(g) For any MLG downlock actuator 

identified during the inspection or 

maintenance records review required by 

paragraph (f) of this AD, or for which the part 

number cannot be determined: Within 66 

months after the effective date of this AD, 

replace the MLG downlock actuator with a 

modified MLG downlock actuator in 

accordance with the Accomplishment 

Instructions of Fokker Service Bulletin F28/ 

32–163, dated March 8, 2004. 

Note 1: Fokker Service Bulletin F28/32–

163 refers to Dowty Aerospace Hydraulics—

Cheltenham Service Bulletin 32–501R, 

Revision 1, dated September 3, 1998, as an 

additional source of service information for 

modifying the MLG downlock actuator. 

Parts Installation 

(h) As of the effective date of this AD, no 

person may install an MLG downlock 

actuator, P/N 200497005 or 200498005, on 

any airplane. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, has the authority to approve AMOCs 

for this AD, if requested in accordance with 

the procedures found in 14 CFR 39.19. 

(2) Before using any AMOC approved in 

accordance with Sec. 39.19 on any airplane 

to which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

Related Information 

(j) Dutch airworthiness directive 2004–047, 

dated April 20, 2004, also addresses the 

subject of this AD. 

Material Incorporated by Reference 

(k) You must use Fokker Service Bulletin 

F28/32–163, dated March 8, 2004, to perform 

the actions that are required by this AD, 

unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference of this document 

in accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. Contact Fokker Services B.V., 

Technical Services Dept., P.O. Box 231, 2150 

AE Nieuw-Vennep, the Netherlands, for a 

copy of this service information. You may 

review copies at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington; or at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal-register/ 

cfr/ibr-locations.html. 

Issued in Renton, Washington, on February 

15, 2007. 

Stephen Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E7–3168 Filed 2–26–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27335; Directorate 

Identifier 2006–NM–291–AD; Amendment 

39–14962; AD 2007–05–01] 

RIN 2120–AA64 

Airworthiness Directives; 

Construcciones Aeronauticas, S.A., 

(CASA) Model C–212 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as follows: 

On 23 November 2006, Emergency 

Airworthiness Directive 2006–0351–E was 

published requiring an inspection to be 

performed on C–212 aeroplanes having been 

used for Maritime Patrol or other similar low 

altitude operations, due to the fact that, after 

initial examination of the evidences of a 

recent C–212 Maritime Patrol aircraft 

accident, cracks had been found in the centre 

wing lower skin at STA Y=1030. At the time 

of the accident, the aircraft had accumulated 

17,000 flight hours and 7,300 flight cycles. 

The cracks were suspected to be caused by 

fatigue. 

After a more detailed examination in the 

laboratory, it has been determined that the 

initiation of the cracks was produced by 

fretting. 

* * * * * 


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Federal Register / Vol. 72, No. 38 / Tuesday, February 27, 2007 / Rules and Regulations 8611 

The above mentioned cracks, if not timely 

detected, could lead to reduced structural 

integrity of the aircraft. * * * 

* * * * * 

This AD requires actions that are 

intended to address the unsafe 

condition. 

DATES: This AD becomes effective 

March 14, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 14, 2007. 

We must receive comments on this 

AD by March 29, 2007. 

ADDRESSES: You may send comments by 

any of the following methods: 

• DOT Docket Web Site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Fax: (202) 493–2251. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

0001. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

• Federal Rulemaking Portal: http:// 

www.regulations.gov. Follow the 

instructions for submitting comments. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.gov; or in 

person at the Docket Management 

Facility between 9 a.m. and 5 p.m., 

Monday through Friday, except Federal 

holidays. The AD docket contains this 

AD, the regulatory evaluation, any 

comments received, and other 

information. The street address for the 

Docket Office (telephone (800) 647–

5227) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Shahram Daneshmandi, Aerospace 

Engineer, International Branch, ANM–

116, FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; 

telephone (425) 227–1112; fax (425) 

227–1149. 

SUPPLEMENTARY INFORMATION: 

Streamlined Issuance of AD 

The FAA is implementing a new 

process for streamlining the issuance of 

ADs related to MCAI. This streamlined 

process will allow us to adopt MCAI 

safety requirements in a more efficient 

manner and will reduce safety risks to 

the public. This process continues to 

follow all FAA AD issuance processes to 

meet legal, economic, Administrative 

Procedure Act, and Federal Register 

requirements. We also continue to meet 

our technical decision-making 

responsibilities to identify and correct 

unsafe conditions on U.S.-certificated 

products. 

This AD references the MCAI and 

related service information that we 

considered in forming the engineering 

basis to correct the unsafe condition. 

The AD contains text copied from the 

MCAI and for this reason might not 

follow our plain language principles. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Emergency Airworthiness Directive 

2006–0365–E, dated December 4, 2006 

(referred to after this as ‘‘the MCAI’’), to 

correct an unsafe condition for the 

specified products. The MCAI states: 

On 23 November 2006, Emergency 

Airworthiness Directive 2006–0351–E was 

published requiring an inspection to be 

performed on C–212 aeroplanes having been 

used for Maritime Patrol or other similar low 

altitude operations, due to the fact that, after 

initial examination of the evidences of a 

recent C–212 Maritime Patrol aircraft 

accident, cracks had been found in the centre 

wing lower skin at STA Y=1030. At the time 

of the accident, the aircraft had accumulated 

17,000 flight hours and 7,300 flight cycles. 

The cracks were suspected to be caused by 

fatigue. 

After a more detailed examination in the 

laboratory, it has been determined that the 

initiation of the cracks was produced by 

fretting. 

The subject element is identified in Ref. 1 

(C–212 Supplemental Inspection Document 

(SID) C–212–PV–02–SID) as a Principal 

Structural Element (PSE) with No. 57.212.06 

and requested to be inspected at a threshold 

of 20,000 landings (subject to some 

operational constraints defined in Ref. 1) in 

accordance with the inspection method and 

sequence described in Ref. 2 (C–212 

Supplemental Inspection Procedures 

(SIP) C–212–PV–02–SIP), Section 57–10–03. 

Ref. 1 document was made mandatory by 

DGAC-Spain Airworthiness directive Nr. 

02/88 (current status of that AD is revision 

3, dated 4 February 2004). 

Inspection threshold as per AD 02/88 Rev. 

3 remains valid and relevant inspections 

have to be performed in addition to the 

requirements of this Emergency 

Airworthiness Directive (EAD). 

The above mentioned cracks, if not timely 

detected, could lead to reduced structural 

integrity of the aircraft. This EAD, which 

supersedes EASA EAD 2006–0351–E, is 

intended to ensure that no other C–212 

aircraft could be affected by this problem, by 

mandating a one time inspection of the 

subject area, in accordance with the 

requirements under the paragraph 

‘‘Compliance’’ of this EAD (EASA EAD 2006–

0365–E). 

Furthermore, it has been determined that a 

Non Destructive Inspection (NDI) performed 

in accordance with Ref. 2, Section 57–10–03 

could not be sufficient to detect cracks 

initiated by fretting. A complementary 

inspection procedure has been defined, and 

is also required under the paragraph 

‘‘Compliance’’ of this EAD (EASA EAD 2006–

0365–E). 

The corrective action includes a onetime inspection for cracks, and repair if 

necessary. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Relevant Service Information 

EADS–CASA has issued All Operator 

Letter 212–018, Revision 1, dated 

December 1, 2006. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

FAA’s Determination and Requirements 

of this AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between the AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow FAA policies. 

Any such differences are highlighted in 

a Note within the AD. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because after a recent C–212 

Maritime Patrol aircraft accident, fatigue 


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8612 Federal Register / Vol. 72, No. 38 / Tuesday, February 27, 2007 / Rules and Regulations 

cracks were found in the center wing 

lower skin at STA Y=1030. This 

cracking could lead to reduced 

structural integrity of the airplane. 

Therefore, we determined that notice 

and opportunity for public comment 

before issuing this AD are impracticable 

and that good cause exists for making 

this amendment effective in fewer than 

30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2007–27335; 

Directorate Identifier 2006–NM–291–

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2007–05–01 Construcciones Aeronauticas, 

S.A. (CASA): Amendment 39–14962. 

Docket No. FAA–2007–27335; 

Directorate Identifier 2006–NM–291–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective March 14, 2007. 

Affected ADs 

(b) AD 96–07–14, amendment 39–9564, is 

related to this AD. 

Applicability 

(c) This AD applies to Construcciones 

Aeronauticas, S.A., (CASA) Model C–212 

airplanes; all series, all serial numbers; 

certificated in any category. 

Subject 

(d) Wings. 

Reason 

(e) The mandatory continued airworthiness 

information (MCAI) states: 

On 23 November 2006, Emergency 

Airworthiness Directive 2006–0351–E was 

published requiring an inspection to be 

performed on C–212 aeroplanes having been 

used for Maritime Patrol or other similar low 

altitude operations, due to the fact that, after 

initial examination of the evidences of a 

recent C–212 Maritime Patrol aircraft 

accident, cracks had been found in the centre 

wing lower skin at STA Y=1030. At the time 

of the accident, the aircraft had accumulated 

17,000 flight hours and 7,300 flight cycles. 

The cracks were suspected to be caused by 

fatigue. 

After a more detailed examination in the 

laboratory, it has been determined that the 

initiation of the cracks was produced by 

fretting. 

The subject element is identified in Ref. 1 

(C–212 Supplemental Inspection Document 

(SID) C–212–PV–02–SID) as a Principal 

Structural Element (PSE) with No. 57.212.06 

and requested to be inspected at a threshold 

of 20,000 landings (subject to some 

operational constraints defined in Ref. 1) in 

accordance with the inspection method and 

sequence described in Ref. 2 (C–212 

Supplemental Inspection Procedures (SIP) C–

212–PV–02–SIP), Section 57–10–03. 

Ref. 1 document was made mandatory by 

DGAC-Spain Airworthiness directive Nr. 02/ 

88 (current status of that AD is revision 3, 

dated 4 February 2004). 

Inspection threshold as per AD 02/88 Rev. 

3 remains valid and relevant inspections 

have to be performed in addition to the 

requirements of this Emergency 

Airworthiness Directive (EAD). 

The above mentioned cracks, if not timely 

detected, could lead to reduced structural 

integrity of the aircraft. This EAD, which 

supersedes EASA EAD 2006–0351–E, is 

intended to ensure that no other C–212 

aircraft could be affected by this problem, by 

mandating a one-time inspection of the 

subject area, in accordance with the 

requirements under the paragraph 

‘‘Compliance’’ of this EAD (EASA EAD 2006–

0365–E). 

Furthermore, it has been determined that a 

Non Destructive Inspection (NDI) performed 

in accordance with Ref. 2, Section 57–10–03 

could not be sufficient to detect cracks 

initiated by fretting. A complementary 

inspection procedure has been defined, and 

is also required under the paragraph 

‘‘Compliance’’ of this EAD (EASA EAD 2006–

0365–E). 

The corrective action includes a one-time 

inspection for cracks, and repair if necessary. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) For airplanes used for maritime 

operations and all other airplanes on which 

the operator cannot positively determine that 

the airplanes have not been flown more than 

ten percent of flights at altitudes below 3,000 

feet as of the effective date of this AD: 

Perform a Non-Destructive Inspection (NDI) 

and a complementary NDI for cracks at the 

applicable time specified in paragraph 

(f)(1)(i), (f)(1)(ii), or (f)(1)(iii) of this AD. Do 

the inspections as defined in EADS–CASA 

All Operator Letter 212–018, Revision 1, 

dated December 1, 2006. 

Note: For the purposes of this AD, the term 

‘‘maritime operations’’ is defined as airplanes 

which are used for monitoring certain areas 

of water. 

(i) For airplanes having accumulated 5,600 

flight hours or less, and 2,400 landings or 


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Federal Register / Vol. 72, No. 38 / Tuesday, February 27, 2007 / Rules and Regulations 8613 

less, as of the effective date of this AD: 

Perform the inspections before the 

accumulation of 5,600 total flight hours or 

2,400 total landings after the effective date of 

this AD, or within 6 months after the 

effective date of this AD, whichever occurs 

latest. 

(ii) For airplanes having accumulated more 

than 5,600 flight hours but less than or equal 

to 8,000 flight hours, or more than 2,400 

landings but less than or equal to 3,600 

landings, as of the effective date of this AD: 

Perform the inspections before the 

accumulation of 200 flight hours or 100 

landings after the effective date of this AD, 

whichever occurs first. 

(iii) For airplanes having accumulated 

more than 8,000 flight hours or more than 

3,600 landings as of the effective date of this 

AD: Perform the inspections within 14 days 

after the effective date of this AD. 

(2) For airplanes other than those 

identified in paragraph (f)(1) of this AD: 

Perform the NDIs at the applicable time 

specified in paragraph (f)(2)(i), (f)(2)(ii), or 

(f)(2)(iii) of this AD. Do the inspections as 

defined in EADS–CASA All Operator Letter 

212–018, Revision 1, dated December 1, 

2006. 

(i) For airplanes having accumulated 

10,000 flight hours or less, and 10,000 

landings or less as of the effective date of this 

AD: Perform the inspections before the 

accumulation of 10,000 total flight hours or 

10,000 total landings after the effective date 

of this AD, or within 6 months after the 

effective date of this AD, whichever occurs 

latest. 

(ii) For airplanes having accumulated more 

than 10,000 flight hours but less than or 

equal to 15,000 flight hours, or more than 

10,000 landings but less than or equal to 

15,000 landings, as of the effective date of 

this AD: Perform the inspections before the 

accumulation of 200 flight hours or 100 

landings after the effective date of this AD, 

whichever occurs first. 

(iii) For airplanes having accumulated 

more than 15,000 flight hours or more than 

15,000 landings as of the effective date of this 

AD: Perform the inspections within 14 days 

after the effective date of this AD. 

(3) No further flight is allowed if any 

cracks are detected when performing the 

actions specified in paragraphs (f)(1) and 

(f)(2) of this AD. Before further flight, repair 

any cracking found during any inspection 

required by this AD using a method approved 

by either the Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA; or the European Aviation Safety 

Agency (EASA) (or its delegated agent). 

Within 30 days after cracks are detected, or 

within 30 days after the effective date of this 

AD, whichever occurs later, send a detailed 

report of the findings (both positive and 

negative) of the inspections required by 

paragraph (f) of this AD to EADS–CASA for 

evaluation at the following address: EADS–

CASA, Military Transport Aircraft Division, 

Integrated Customer Services, Technical 

Services, Avenida de Aragon 404, 28022- 

Madrid, Spain; telephone 34–91–624–6306; 

fax 34–91–585–5505. E-mail: MTA, 

TechnicalService@casa.eads.net. In any case, 

a confirmation of the accomplishment of this 

inspection is required to be sent to EADS–

CASA. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: 

(1) Compliance Time: For certain airplanes, 

the compliance time required by the MCAI or 

service information for performing the nondestructive inspections is before further 

flight; however, to avoid inadvertently 

grounding airplanes, this AD requires 

performing those inspections within 14 days 

after the effective date of this AD. 

(2) Repair: Although the MCAI or service 

information does not include a repair 

procedure for cracking, this AD requires the 

repair of any cracking per the FAA, EASA, 

or its delegated agent. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

Send information to ATTN: Shahram 

Daneshmandi, Aerospace Engineer; 1601 

Lind Avenue, SW., Renton, WA 98057–3356; 

telephone (425) 227–1112; fax (425) 227–

1149. Before using any AMOC approved in 

accordance with § 39.19 on any airplane to 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. Before using any AMOC approved in 

accordance with § 39.19 on any airplane to 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act, 

the Office of Management and Budget (OMB) 

has approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to MCAI EASA Emergency 

Airworthiness Directive 2006–0365–E, dated 

December 4, 2006; and EADS–CASA All 

Operator Letter 212–018, Revision 1, dated 

December 1, 2006, for related information. 

Material Incorporated by Reference 

(i) You must use EADS–CASA All Operator 

Letter 212–018, Revision 1, dated December 

1, 2006, to do the actions required by this 

AD, unless the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Construcciones 

Aeronauticas, S.A., Getafe, Madrid, Spain. 

(3) You may review copies at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington 98057–

3356; or at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call (202) 741–6030, or go 

to: http://www.archives.gov/federal-register/ 

cfr/ibr-locations.html. 

Issued in Renton, Washington, on February 

16, 2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–3164 Filed 2–26–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–26496 Directorate 

Identifier 2006–CE–81–AD; Amendment 39–

14958; AD 2007–04–25] 

RIN 2120–AA64 

Airworthiness Directives; Alpha 

Aviation Design Limited R2160 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

issued by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as a deficiency in compliance 

with 14 CFR 23.967(d). There have been 

instances indicating that production 

aircraft may not have a metal barrier 

between the cabin and the fuel tank bay. 

Lack of a barrier could allow flammable 

fuel vapors to enter the cabin. We are 

issuing this AD to require actions to 

correct the unsafe condition on these 

products. 

DATES: This AD becomes effective April 

3, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of April 3, 2007. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the Docket 

Management Facility, U.S. Department 


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